Mounting for adjustably holding a guide vane carrier in a multistage gas turbine

ABSTRACT

The guide vane carrier is slidably mounted by means of a flange in the groove of the turbine intermediate part while the eccentrically placed adjustable supports are mounted so as to effect a horizontal and/or vertical adjustment of the guide vane carrier on the intermediate part upon rotation of the eccentrically formed bolts.

United States Patent lnventor Ferdinand Zerlauth Winterthur, Switzerland Appl. No. 820,437

Filed Apr. 30, 1969 Patented June 15, 1971 Assignee Sulzer Brothers Ltd.

Winterthur, Switzerland Priority May 20, 1968 Switzerland 7490/68 MOUNTING FOR ADJUSTABLY HOLDING A GUIDE VANE CARRIER IN A MULTISTAGE GAS TURBINE [56] References Cited UNITED STATES PATENTS 1,670,452 5/1928 Kaehler 415/138 2,625,013 1/1953 Howard et a1. 60/3932 2,530,908 11/1950 R 415/136 2,695,767 11/1954 Land et a1 415/136 3,363,416 1/1968 Heybyrne 60/3932 X 3,387,820 6/1968 Smith 415/219 3,459,460 8/1969 Kopp 60/3932 X 3,498,727 3/1970 Martin, Jr. et a1. 415/136 Primary Examiner Henry F. Raduazo Attorney-Kenyon and Kenyon, Reilly, Carr & Chapin 6clalms6 Drawing Flgs' ABSTRACT: The guide vane carrier is slidably mounted by U.S.Cl 415/137 means of a flange in the groove of the turbine intermediate Int.Cl F01d 9/00, part while the eccentrically placed adjustable supports are FOld 25/26 mounted so as to effect a horizontal and/or vertical adjust- Field of Search 415/ 136, ment of the guide vane carrier on the intermediate part upon 219, 137, 138; 60/3932, 3916, 39.31 rotation ofthe eccentrically formed bolts.

7 13 a8 J9 40 a 35 45 49 51 52 2 3 i 7* PATENTEDJUM 519m 3584.967.

sum 1 OF 5 FIQ. :L,

INVENTOR. FfPDl/Vfl/VD Z EFL AUTA/ PATENTEUJUNI 51ml 3.5841967 SHEET 2 [1F 5 63b 63a 29 61. 63 Q4 Fig.3 Fig. 2

Inventor- FERDINAND ZEQLAU TH 147" PNEYS PATENTEUJUM 5m 3584867 sum 3 CF 5 Inventor FERDINAND ZE/QLQUTH MOUNTING FOR ADJUSTABLY HOLDING A GUIDE VANE CARRIER IN A MULTISTAGE GAS TURBINE This invention relates to a mounting for a guide vane carrier in a gas turbine and more particularly to an adjustable mountmg.

Heretofore, in the case of gas turbines, the mountings of guide vane carriers within the turbines have often caused difficulties in that as a result of the great differences that occur due to the hot operating gases in the turbine, large heat expansions and thermal stresses have occurred. Because of this, the guide vane carriers have sometimes been deformed relative to the cooperating rotors of the turbines or have been dislocated. When this has occurred, the possibility has arisen that the blade carrying rotor discs rotating within the guide vane carrier between the guide vane may graze the carrier or the guide vanes.

Accordingly, it is an object of the invention to avoid misalignment of the guide vane carrier and the blade carrying rotor discs o'fa gas turbine.

It is another object of the invention to mount a guide vane carrier in an adjustable manner within a turbine.

It is another object of the invention to provide a simple means for adjustably mounting a guide vane carrier in a turbine.

It is another object of the invention to provide a mounting which allows thermal expansion of a guide vane carrier without requiring adjustments to the vane clearances.

Briefly, the invention provides a mounting for a guide vane carrier ofa gas turbine which permits the guide vane carrier to be adjusted and centered with respect to the axis of the turbine. The mounting provides for mounting of the guide vane carrier at one end in a casinglike intermediate piece which is secured to a central housing of the turbine at a downstream end while the opposite free end is centered relative to the rotor of the turbine in the region of the foremost guide vane ring, for example, by the aid of a centering support fastened upstream to a front housing of the turbine. By mounting the guide vane carrier to the intermediate part which is situated downstream of the inlet of the hot combustion gases and is thus in a region in which the housing is cooler, the above mentioned effects of the large temperature differences that occur are decisively mitigated. Consequently, heat expansions occur to a much smaller degree at the point ofmounting.

The mounting of the guide vane carrier to the intermediate part is further formed so that the carrier is slidably received in the part and is secured to the part by a plurality of eccentrically mounted supports so as to permit',adjusting of the blade clearance in the region of the last turbine stage.

These and other objects and advantages of the invention will become more apparent from the following detailed description and appended claims taken in conjunction with the accompanying drawings in which:

FIG. 1 schematically illustrates a turbine construction incorporating a mounting according to the invention;

FIG. 2 illustrates a partial cross-sectional view of the mounting of a guide vane carrier to a central housing of the turbine of FIG. 1 according to the invention;

FIG. 3 illustrates a view taken in the direction indicated by the arrow A in FIG. 2;

FIG. 4 illustrates a view taken on line IV-IV of FIG. 3;

FIG. 5 illustrates a view taken on line V-V of FIG. 3; and

FIG. 6 illustrates a view taken on line VI-VI of FIG. 5.

Referring to FIG. 1, the two-shaft multistage gas turbine is constructed with an induction housing 1, a compressor 2, a diffuser 6, a compressor drive turbine 8 within a combustion chamber system 9, a useful power turbine 25 within a housing 45, and a waste-gas housing 52in coaxial alignment.

The induction housing 1, shown in outline and divided along a horizontal axial plane for simplicity, is connected in the direction of flow to the compressor 2, also shown in outline for simplicity. In addition, the compressor 2 has a rotor bearing 4 on the induction housing side which is supported on a machine bed 23 in a suitable manner.

The compressor 2 has a housing which surrounds a guide vane support 3 and which merges into a front housing 7 surrounding the diffuser 6. In addition, the compressor 2 includes a rotor-l0 (the last stage 11 of the rotor 10 being shown between its last two guide vane stages 12, 13) which ends in a connection part 14 and which is adjoined at the downstream face by a transition disc 15 within the combustion chamber system 9 to connect the compressor 2 to the drive turbine 8. A tension-anchor or tie rod 16 is anchored in the connection part 14 so as to mount and hold together, with the aid ofa tie rod head 19, a plurality of rotor discs 17 and a shaft journal 18 of the drive turbine 8. For purposes of clarity, the details of this anchorage is not shown; however, it is noted that any suitable anchorage as is known can be used.

The individual rotor discs 17 are similar to one another and are fastened to one another and to the transition disc 15 and also to the shaft journal 18, as is known, by radial serrations. The rotor discs 17 serve to carry rotor vanes or blades 20.

The shaft journal 18 is mounted in shaft bearings 21 which are supported in a bearing housing 22. The bearings 4, 21 are further supported in suitable mountings on a support bed 23.

Each bearing housing 22 is also provided with two labyrinth seals 26 while additional labyrinth seals 27, 28 for sealing the rotor 10 are disposed between the transition disc 15 and a centering support 32 having a foremost conical portion, which is secured to the diffuser housing 7 and between the shaft journal 18 and an adapter piece 37, respectively.

The rotor discs 17 of the turbine 8 are surrounded by a guide vane carrier 29 in which a plurality of guide vanes 30 are fastened. Each of the guide vanes ends in a guide vane ring 31 which is disposed between the individual rotor discs 17 and which forms the inner limit of the flow channel for the combustion gases in the region of the turbine 8. Moreover, the first guide vane ring 310 in the path of flow is connected with the adjacent hollow cylinder centering support 32. The centering support 32 thus also serves to center the inflow end of the guide vane carrier 29 relative to the rotor 10. Also, in order to direct the hot combustion gases coming out of the combustion chamber 9 into the turbine 8, an inflow housing 33, as is known, is disposed at the upstream end of the turbine.

The guide vane carrier 29 is further mounted at the downstream end to a casinglike intermediate part 34 which in turn is secured to a central housing 35 situated farther downstream.

The central housing 35 has internal parts which cooperate with the bearing housing 22 and an additional adapter piece 37 to define the inner limit of the flow channel 38 for the gases. The adapter piece 37 serves to bridge over the space between the bearing housing 22 and the last rotor disc 17 of the compressor turbine 8. The flow channel 38 is delimited at the outside, as far as the central housing 35, by a sheet metal casing 39 which is secured to and between the guide vane carrier 29 and the central housing 35. In addition, a pair of conical casing parts 40, 41 which are disposed in opposite sign to each other extend from the casing 39 to further define the flow channel 38.

By securing the guide vane carrier 29 to the relatively cool regions at the central housing 35 and at the front diffuser housing 7, the heat expansion and heat stresses resulting from temperature differences are substantially decreased. Thus, the danger of deformation and of a dislocation of the guide vane carrier 29 relative to the rotor 10 is, at least, substantially diminished.

In this coaxial shaft turbine, a second bearing housing 22 adjoins the downstream end of the central housing 35. This second bearing housing 22 mounts the inflow side of a rotor shaft journal 42 of the useful power turbine 25 and is surrounded by a casing 44 which serves to define the flow channel 38 as by a housing part 45. The useful power turbine 25, for example, a two-stage turbine, is composed of a rotor 47 mounted in a bearing 46, rotor discs 17 which carry blades 24 similar to the blades 20 described above (at least having the same blade root and blade profile as above), and the shaft journal 42. These components, as with the above turbine 8,

are held together by a tension-anchor or tie rod 43 which is anchored in the rotor part 47 and which has a tie rod head 19. The turbine rotor 47 is surrounded by a guide vane carrier 49 which carries fixed guide vanes 50.

In addition. a waste-gas diffuser 51 is disposed adjacent the guide vane carrier 49 to surround the rotor 47. This diffuser 51 has an outlet which opens into the waste-gas housing 52.

Finally, the rotor 47 is connected via a coupling 53 to a shaft 54 ofa work machine (not shown).

Referring to FIGS. 2 and 3, the guide vane carrier 29 is secured to the intermediate part 34 by means of three eccentric and adjustable supports 63 which permit exact adjustment to the correct clearance between the vanes of the carrier 29 and of the rotor. As shown, the intermediate part 34 which can be a hollow cylindrical or conical two part casing has an annular extension 60 at the free end which forms an annular groove 61 (FIG. 4) over a wide range of its periphery. Also, the guide vane carrier 29 which is split along a horizontal axial plane has a flange 62 located on the end which is slidably received within the groove 61 ofthe extension 60.

Referring to FIGS. 3, and 6, the adjustable supports 63 are disposed in the horizontal plane of separation as well as in the middle of the lower half of the guide vane carrier 29. In order to receive these supports 63, the annular extension 60 is interrupted in these locations so as to form a simple abutment plate 60a (FIG. 5). In addition, two webs 64 are welded to the guide vane carrier 29 at each support 63 to extend radially of the carrier in order to define a flange 66 having a bore 65.

Referring to FIGS. 5 and 6, a slide 67 of rectangular cross section is fitted between each pair ofwebs 64 to receive a bolt 68 having a central axis 69 which is substantially parallel to the carrier axis. The slide 67 is positioned between the webs 64 by means of a bolt 70 which is threaded into the bores 65 and a spacer sleeve 71 surrounding the bolt 70. The spacer sleeve 71 is dimensioned so that the spacing between the flanges 66 ofthe webs 64 corresponds to the dimensions ofthe slide 67.

The bolt 68 further has an eccentric head oflarger diameter which has an axis 72 displaced from the central axis 69 and a flange 74 at the end. The eccentric head also fits into a bore 75 in a connection plate 76 which is fastened by threaded bolts 78 through respective bores 79 in the annular extension 60 at points spaced from the supports 63 (FIG. 4).

Referring to FIG. 5, the flange 74 of the bolt head is also provided with recesses 80 in which a suitable tool can engage in order to turn the bolt 68. In order to prevent accidental turning of the bolt 68, a cover plate 82 is secured over the flange 74 by means of screws 81 which press the plate 82 against the flange 74 and, in turn, press the flange 74 against the connection plate 76. y

In order to adjust the vane clearance, the bolts 68 of the respective supports 63 are turned so as to obtain a movement ofthe axes 69, 72 ofeach bolt 68 relative to each other, for example, as indicated by the arrows 83 in FIG. 6. Since the central axis 69 is able to move with the guide vane carrier 29 via the bolt 68, slide 67 and webs 64 while the axis 72 remains in place relative to the intermediate part 34, via the eccentric bolt head, connection plate 76 and bolts 78, the carrier 29 is displaced relative to the intermediate part 34.

An adjustment of the guide vane carrier 29 in the horizontal direction relative to the intermediate part 34 is obtained by adjustment of the support 63a (FIG. 3) while an adjustment in the vertical direction is obtained by adjustment of the two supports 63b (FIG. 3) in the horizontal plane of separation.

It is noted that in the event ofa large heating up of the carrier 29, the mounting permits uniform unhindered expansion of the carrier 29 in a radial direction. This allows the flange 62 to penetrate deeper i.e. expand radially into the annular groove 61 while the webs 64 at the supports 63 are allowed to shift on the slide 67 without changing the adjustment in the vane clearance.

What I claim is:

1. In combination,

a guide yane carrier of a multistage gas turbine, a plurality of rows of guide vanes fastened within said carria casinglike intermediate part secured at one end to one end of said guide vane carrier,

a central housing of the multistage gas turbine secured to an opposite end of said intermediate part downstream of said guide vane carrier, and

means mounting the opposite end of said guide vane carrier for centering said guide vane carrier relative to a rotor passing therethrough.

2. The combination as set forth in claim I wherein said means includes a centering support mounted on a front housing of the gas turbine.

3. The combination as set forth in claim I which further comprises a plurality ofperipherally mounted supports on said one end of said intermediate part slidably connecting said one end ofsaid guide vane carrier to said intermediate part.

4. A mounting for securing a guide vane carrier having a flange at one end thereof to an intermediate part of a gas turbine having an interrupted extension on one end forming an annular groove slidably receiving said flange, said mounting comprising a plurality of supports, each support including a slide, means connected to said flange for guiding said slide radially of said carrier and means connected to said extension for moving said slide relative to said extension to displace said carrier relative to said intermediate part.

5. A mounting as set forth in claim 4 wherein said means for guiding said slide include a pair of radially extending webs on said flange, said slide being slidably mounted between said webs.

6. A mounting as set forth in claim 4 wherein said means for moving said slide includes a bolt having a central axis received in said slide and an eccentric head having an axis offset from said central axis, and a connection plate secured to said extension and having a bore receiving said eccentric head whereby turning of said bolt effects a relative movement of said carrier to said intermediate part. 

1. In combination, a guide vane carrier of a multistage gas turbine, a plurality of rows of guide vanes fastened within said carrier, a casinglike intermediate part secured at one end to one end of said guide vane carrier, a central housing of the multistage gas turbine secured to an opposite end of said intermediate part downstream of said guide vane carrier, and means mounting the opposite end of said guide vane carrier for centering said guide vane carrier relative to a rotor passing therethrough.
 2. The combination as set forth in claim 1 wherein said means includes a centering support mounted on a front housing of the gas turbine.
 3. The combination as set forth in claim 1 which further comprises a plurality of peripherally mounted supports on said one end of said intermediate part slidably connecting said one end of said guide vane carrier to said intermediate part.
 4. A mounting for securing a guide vane carrier having a flange at one end thereof to an intermediate part of a gas turbine having an interrupted extension on one end forming an annular groove slidably receiving said flange, said mounting comprising a plurality of supports, each support including a slide, means connected to said flange for guiding said slide radially of said carrier and means connected to said extension for moving said slide relative to said extension to displace said carrier relative to said intermediate part.
 5. A mounting as set forth in claim 4 wherein said means for guiding said slide include a pair of radially extending webs on said flange, said slide being slidably mounted between said webs.
 6. A mounting as set forth in claim 4 wherein said means for moving said slide includes a bolt having a central axis received in said slide and an eccentric head having an axis offset from said central axis, and a connection plate secured to said extension and having a bore receiving said eccentric head whereby turning of said bolt effects a relative movement of said carrier to said intermediate part. 